Methods and systems for monitoring rotor blades in turbine engines

ABSTRACT

A method for determining an arrival-time of a rotor blade in a turbine engine that includes the steps of: having an RF reader attached to a stationary surface in the turbine engine; having an RF tag attached to a first region of the rotor blade; having a reference RF tag attached to a rotating structure near the RF tag; in relation to a first revolution of the rotor blade occurring during the operation of the turbine engine, collecting an arrival-time for each of the RF tag and the reference RF tag with the RF reader via an RF monitoring process; comparing the arrival-time of the RF tag to the arrival-time of the reference RF tag to determine an arrival-time test result for the first region of the rotor blade for the first revolution.

BACKGROUND OF THE INVENTION

This present application relates generally to methods and systems forimproving the efficiency and operation of turbine engines, which, asused herein, is meant to include all types of turbine or rotary engines,including gas turbines, steam turbine engines, and others. Morespecifically, but not by way of limitation, the present applicationrelates to methods and systems for monitoring rotor blades, includingthe vibrational response thereof via blade timing.

Turbine engines include rows of rotor blades interact with ahigh-velocity working fluid that causes the blades to rotate about acentral axis. Such blades are exposed to the harsh conditions within theengine and must endure extreme mechanical and thermal loads duringengine operation. Because of this, the design of rotor blades is anexacting challenge. New rotor blade designs must be effectivelyvalidated through rigorous upfront testing. Further, during use, thehealth of rotor blades must be monitored closely. The failure of a rotorblade during operation can cause catastrophic damage to a turbineengine. Such blade failures can be predicted and, thereby, avoidedthrough rigorous upfront testing and/or health monitoring thataccurately detects blade degradation or defects. For example, anomaliesin the vibrational response of rotor blades to operating conditions canbe an indicator of high strain levels or crack formation in the blades.

One common approach to measuring the vibrational response of rotorblades during operation is known as blade tip timing or, as used herein,“blade timing”. Generally, though, the availability of such testing issomewhat limited due to the high cost associated with it. Further, giventhe limitations associated with known methods of measuring blade timing,the data can often be unreliable. Of course, one alternative is to shutdown the turbine engine to visually inspect the rotor blades fordefects. This type of inspection, though, has its own drawbacks in thatit provides no information about the stresses occurring duringoperation, is also prone to unreliability, and is costly due to thelabor requirements and need to shut down the engine. As a result, thereis a continuing need for improved methods and systems pertaining torotor blade monitoring and diagnostics, particularly as it relates toimproving the cost-effectiveness and reliability of blade timingtechniques.

BRIEF DESCRIPTION OF THE INVENTION

The present application thus describes methods and systems fordetermining an arrival-time of a rotor blade in a turbine engine thatincludes the steps of: having a radio frequency (“RF”) reader attachedto a stationary surface in the turbine engine; having a radio frequencyidentification tag (“RF tag”) attached to a first region of the rotorblade; having a reference radio frequency tag (“reference RF tag”)attached to a rotating structure near the RF tag; in relation to a firstrevolution of the rotor blade occurring during the operation of theturbine engine, collecting an arrival-time for each of the RF tag andthe reference RF tag with the RF reader via an RF monitoring process;comparing the arrival-time of the RF tag to the arrival-time of thereference RF tag to determine an arrival-time test result for the firstregion of the rotor blade for the first revolution.

These and other features of the present application will become apparentupon review of the following detailed description of the preferredembodiments when taken in conjunction with the drawings and the appendedclaims.

BRIEF DESCRIPTION OF THE DRAWINGS

These and other objects and advantages of this invention will be morecompletely understood and appreciated by careful study of the followingmore detailed description of exemplary embodiments of the inventiontaken in conjunction with the accompanying drawings, in which:

FIG. 1 is a schematic representation of an exemplary gas turbine enginein which embodiments of the present application may be used;

FIG. 2 is a sectional view of a compressor in a gas turbine engine inwhich embodiments of the present application may be used;

FIG. 3 is a sectional view of a turbine in a gas turbine engine in whichembodiments of the present application may be used;

FIG. 4 is a schematic representation of an exemplary rotor blade showingthe placement of RF tags and the relative location of an RF readeraccording to an exemplary embodiment of the present application;

FIG. 5 is a schematic representation of an RF system according to anexemplary embodiment of the present application;

FIG. 6 shows an exemplary time domain plot demonstrating a method inaccordance with the present application;

FIG. 7 shows an exemplary time domain plot demonstrating an alternativemethod in accordance with the present application;

FIG. 8 is a schematic representation of an exemplary rotor blade showingthe placement of RF tags and the relative location of an RF readeraccording to an alternative embodiment of the present application; and

FIG. 9 shows an exemplary computer system or controller in accordancewith an embodiment of the present application.

DETAILED DESCRIPTION OF THE INVENTION

By way of background, FIG. 1 illustrates a schematic representation of agas turbine engine 100. In general, gas turbine engines operate byextracting energy from a pressurized flow of hot gas that is produced bythe combustion of a fuel in a stream of compressed air. As illustratedin FIG. 1, gas turbine engine 100 may be configured with an axialcompressor 106 that is mechanically coupled by a common shaft or rotorto a downstream turbine section or turbine 110, and a combustor 112positioned between the compressor 106 and the turbine 110. Note that theinvention of the following disclosure may be used in all types ofturbine engines, including gas turbine engines, steam turbine engines,aircraft engines, and others. Hereinafter, the invention will bedescribed in relation to a gas turbine engine. This description isexemplary only and not intended to be limiting in any way.

FIG. 2 illustrates a view of an exemplary multi-staged axial compressor118 that may be used in a gas turbine engine. As shown, the compressor118 may include a plurality of stages. Each stage may include a row ofcompressor rotor blades 120 followed by a row of compressor statorblades 122. Thus, a first stage may include a row of compressor rotorblades 120, which rotate about a central shaft, followed by a row ofcompressor stator blades 122, which remain stationary during operation.The compressor stator blades 122 generally are circumferentially spacedone from the other and fixed about the axis of rotation. The compressorstator blades 122 generally extend from an attachment with a compressorcasing 123. The compressor rotor blades 120 are circumferentially spacedand attached to the shaft such that when the shaft rotates duringoperation, the compressor rotor blades 120 rotate about it. As one ofordinary skill in the art will appreciate, the compressor rotor blades120 are configured such that, when spun about the shaft, they impartkinetic energy to the air or working fluid flowing through thecompressor 118. The compressor 118 may have many other stages beyond thestages that are illustrated in FIG. 2. Additional stages may include aplurality of circumferential spaced compressor rotor blades 120 followedby a plurality of circumferentially spaced compressor stator blades 122.

FIG. 3 illustrates a partial view of an exemplary turbine section orturbine 124 that may be used in the gas turbine engine. The turbine 124also may include a plurality of stages. Three exemplary stages areillustrated, but more or less stages may be present in the turbine 124.A first stage includes a plurality of turbine buckets or rotor blades126, which rotate about the shaft during operation, and a plurality ofnozzles or turbine stator blades 128, which remain stationary duringoperation. The turbine stator blades 128 generally are circumferentiallyspaced one from the other and fixed about the axis of rotation. Theturbine stator blades 128 generally extend from an attachment with asurrounding turbine casing 129. The turbine rotor blades 126 may bemounted on a turbine disc or wheel (not shown) for rotation about thecentral axis or shaft (not shown). Second and third stage of the turbine124 also are illustrated, each of which includes a plurality ofcircumferentially spaced turbine stator blades 128 followed by aplurality of circumferentially spaced turbine rotor blades 126, whichare also mounted on a turbine wheel for rotation. It will be appreciatedthat the turbine stator blades 128 and turbine rotor blades 126 lie inthe hot gas path of the turbine 124. The direction of flow of the hotgases through the hot gas path is indicated by the arrow. As one ofordinary skill in the art will appreciate, the turbine 124 may have manyother stages beyond that shown in FIG. 3.

In use, the rotation of compressor rotor blades 120 within the axialcompressor 118 may compress a flow of air. In the combustor 112, energymay be released when that compressed air is mixed with a fuel andignited. The resulting flow of hot gases from the combustor 112 then maybe directed over the turbine rotor blades 126, which may induce therotation of the turbine rotor blades 126 about the shaft, thustransforming the energy of the hot flow of gases into the mechanicalenergy of the rotating blades and, because of the connection between therotor blades in the shaft, the rotating shaft. The mechanical energy ofthe shaft may then be used to drive the rotation of the compressor rotorblades 120, such that the necessary supply of compressed air isproduced, and also, for example, a generator to produce electricity.

As discussed above, it is important for rotor blades to be tested andmonitored closely, as blade health affects engine efficiency andperformance and a failure of even a single blade can cause severedamage. Such consequences can be avoided if data indicative of strainlevels, crack formation, and other rotor blade defects can be accuratelycollected and monitored. Generally, though, the availability of suchdata is limited due to the expense of collecting it. Further, givenconventional collection methods, the data can prove unreliable. As aresult, there is a continuing need for enhanced methods and systemspertaining to rotor blade monitoring and diagnostics, particularly as itrelates to improving the cost-effectiveness and reliability of bladetiming techniques.

Toward this objective, the present disclosure proposes to integratecertain aspects of radio frequency identification (or “RFID”) technologyinto particular methods and systems for monitoring rotating blades inturbine engine, for example, gas and steam turbines. By way ofbackground, radio frequency identification or RFID tagging is a knownmethod of identification, and various RFID structures, circuits, andprogramming protocols are known in the art and commercially available.While early RFID systems were developed utilizing relatively largepackage sizes, which limited the products on which they could be used,more recent RFID tags have become much smaller so that they may bereadily incorporated in a variety of products and applications. Aconventional RFID system may include a radio frequency (or “RF”) readerthat produces or emits an RF signal to create an interrogation field.The RFID system also includes one or more RF tags, each of which mayinclude a semiconductor chip having RF circuits, logic, memory, and/oran antenna. The RF tags function in response to the RF signal emitted bythe RF reader. That is, when the RF tag enters the interrogation fieldcreated by the RF reader, an RF inlay in the RF tag becomes stimulatedand induces the RF tag to emit a return RF signal that is then receivedby the RF reader. The return RF signal may be demodulated by the RFreader to recover information stored in the RF tag.

RF tags may be characterized as “active” or “passive”. Active RF tagsuse internal batteries to power their circuits. An active tag also usesits battery to broadcast radio waves to an RF reader. Active tagsgenerally broadcast high frequencies from 850 MHz to 5.8 GHz that can beread 100 feet or more away by the RF reader. Passive RF tags rely on theRF reader as their power source. Passive RF tags are generally read atcloser distances and have lower production costs. In general, either tagworks in the same way: 1) data stored within an RF tag's microchip waitsto be read; 2) the tag's antenna receives electromagnetic energy from anRFID RF reader's antenna; 3) using power from its internal battery—inthe case of active tags—or power harvested from the electromagneticfield created by the RF signal emitted by the RF reader—in the case ofpassive tags—the RF tag sends radio waves back to the RF reader; and 4)the RF reader receives the return signal from the RF tag and interpretsthe frequencies as meaningful data.

The present application relates to a type of rotor blade testing ormonitoring known as blade tip timing, which will be referred to hereinas “blade timing”. Blade timing is a technique that measures the precisetime of arrival (or simply, “arrival-time”) of a rotor blade when therotor blade reaches predetermined location in the rotational path therotor blade makes within the engine. In general, blade timing functionsby detecting small variations in the time it takes for a rotor blade to“arrive” at the defined location. From these small variations, thevibrational response of the rotor blade can be calculated.

To measure arrival-time, conventional blade timing techniques generallyrely on sensors capable of detecting the passing rotor blade and, fromthat, determine the precise time the rotor blade arrives at the definedlocation. To be successful, this must be done with extremely high timeresolution. Most common approaches employ laser or light probes, whileother known techniques use capacitance probes, magnetic pick-ups,reluctance probes, or other sensors capable of detecting the presence ofa passing rotor blade. Conventional blade timing methods, thus,generally rely a stationary sensing device or probe that detects therotor blade to determine the timing of its arrival, or its arrival-time.Using an array of such sensors, the collected arrival-time data can bepost-processed via known algorithms to calculate the vibrationalresponse of the rotor blade, including its frequency and amplitude, asthe turbine engine operates.

However, there are several shortcomings with traditional blade timingtechniques. For example, they can be difficult and costly to implementand the data they produce can be unreliable. Once reason for this is thefrequent absence of a definitive triggering feature on a rotor blade.That is, known blade timing techniques function by detecting the arrivalof the rotor blade by detecting the arrival of a specific recognizablepart or feature (i.e., “triggering feature”) on the passing rotor blade.As will be appreciated, it is necessary for such triggering features tobe a distinct, unmistakable surface feature that is present on each ofthe rotor blades and detectable by the sensor with high time resolution.This is needed because, in order to post-process time domain signals,the data stream must have a distinctive, fast-acting, sizable variationthat can be used by the algorithms. In many cases, rotor blades lackthis type of feature. This is made worse when several such triggeringfeatures are needed on each rotor blade, as often blade timing data canbe enhanced if the arrival-time for multiple areas on each rotor bladeis measured.

When suitable triggering features are not available on the rotor blade,the blade may have to be modified to create them. Such modifications,however, are typically costly and can be time consuming to produce andresult in physical degradation to the rotor blade that shortens itsusable life. Thus, these types of modification are undesirable, yet theyare often unavoidable given the lack of available alternatives.

In addition, the laser probes and other sensors that are typically usedin conventional blade timing systems are typically expensive andapplication-specific (i.e., not interchangeable or reusable). Further,due to the extreme temperatures and operating conditions within aturbine engine, the sensor hardware must be air-cooled during operation,which increases implementation costs and makes extended use impractical.

Turning to the present disclosure, systems and methods are proposed thatuse aspects of RFID technology to perform blade timing. As will be seen,embodiments of the present disclosure may collect arrival-time data,which is usable in standard post-processing algorithms, in a manner thatimproves data accuracy and reliability. Further, because the systems andmethods of the present disclosure eliminate the need for expensiveprobes and air cooling, as well as the need for triggering features,blade timing may be more cost-effective and flexibly applied acrossdifferent turbine engine sizes and types.

Instead of the conventional probes and triggering features of knownsystem, the present disclosure proposes affixing an RF tag to a rotorblade and then monitoring the RF tag in a particular way via an RFreader. By way of example, FIG. 4 schematically illustrates a rotorblade 150 as may be used within a turbine engine, for example, withinthe compressor section. The rotor blade 150 generally has severalorienting features, which include an airfoil 152 that extends radiallyfrom a root 155. The airfoil 152 includes a concave pressure sidewall orpressure side 153 and a circumferentially or laterally opposite, convexsuction sidewall or suction side 154. Both the pressure side 153 and thesuction side 154 extend axially between a leading edge 156 and trailingedge 158. Further, the pressure side 153 and the suction side 154 extendin the radial direction between the root 155 and a radially outer bladetip (or simply “outer tip”) 159.

According to example embodiments of the present disclosure, an RF tag160 is affixed or bonded per conventional means to one or more locationson the rotor blade 150. As shown in FIG. 4 (though not depicted toscale), an RF tag 160 is applied to two different locations: 1) theapproximate mid-area of the suction side of the airfoil 152; and 2) nearthe outer radial edge of the suction side of the airfoil 152 near theleading edge 156. These locations are exemplary, as there are otherlocations on a rotor blade where monitoring the information that may becollected by these tags might be advantageous. As described, the RF tag160 may include conventional circuitry and an antenna 162 for receivingand transmitting data. As an example, the RF tag 160 may be affixed tothe rotor blade 150 by being laminated between outer sheets or layers orcoatings so that the electronic features of the RF tag 160 are protectedfrom the conditions within the turbine engine. Other ways for affixingthe RF tag 160 to the rotor blade 150, such as thermal spray deposition,are also possible.

Within the compressor or turbine, RF tags 160 may be applied to each ofthe rotor blades in a particular row or rows, or in accordance withother embodiments, only selected blades may be monitored with a row asrepresentative of the overall health of the row. As explained morebelow, an RF reader 166 may be suitably provided within the compressoror turbine at a distance so that it is able to read the RF tags 160 onthe rotating blades as they pass by. In accordance with preferredembodiments, the RF tag 160 is a passive RF tag so that it communicateswith the RF reader 166 without requiring an internal power supply. TheRF tag 160 may be small and configured to be minimally intrusive andable to withstand the harsh turbine environment for suitable durations.As will be appreciated, the RF tag 160 includes circuitry that allows itto receive the RF wave transmitted by an antenna of the RF reader 166.Once received, the RF tag may be configured to alter the frequency ofthe RF wave to a known or expected frequency so that the return signalidentifies the particular RF tag. Other conventional ways foridentifying the source of an RF return signal may also be used.

With reference now to FIG. 5, an exemplary RF system 180 is provided inaccordance with aspects of the present disclosure. The RF system 180,which may also be referred to as an RF blade timing system, may operatein a turbine engine environment that, for example, includes a row ofstator blades 182 and rotor blades 181. The stator blades 182 areattached to a casing 184 and remain stationary, while the rotor blades181 are attached to a rotor disc and rotate about the central axis ofthe engine. According to exemplary embodiments, the RF system 180includes one or more RF tags 160 affixed to one or more of the rotorblades 181. The RF tags 160 may be passive. The RF system 180 furthermay include one or more RF readers 166. Each of the RF readers 166 maybe mounted per conventional means to any non-rotating surface within theturbine engine that resides a suitable distance from the rotating RFtags 160 during operation. As shown, for example, the RF reader 166 maybe attached to a stator blade 182, such as, for example, one of thecompressor stator blades 122 or turbine stator blades 128 shown in FIGS.1 through 3. Alternatively, the RF reader 166 may be attached to thecasing 184, for example, the compressor casing 123 or turbine casing 129shown in FIGS. 1 through 3.

As described above, the RF reader 166 may function by producing an RFwave or signal 190 that creates an electromagnetic interrogation field.The RF reader may also be configured to receive a return RF signal 191from the RF tags 160. It should be appreciated that the RF reader 166 ofthe present disclosure includes cases in which the describedfunctionality of the RF reader 166 is achieved via multiple devices atdifferent locations—such as one device to generate the RF signal andanother to receive the return RF signals—and the description andillustration of a single device as the RF reader 166 is exemplary only.The RF tags 160 may be configured to produce the return RF signal 191 inresponse to entering the interrogation field created by the RF reader166.

With reference also to FIG. 6, an exemplary embodiment of the presentdisclosure includes an RF system, such as the above-described RF system180, which functions in the following manner. For the sake of clarity,exemplary operation of this embodiment will be described in reference toa single “RF reader” that functions in relation to a single “RF tag”affixed to a single “rotor blade”. It should be appreciated, however,that in use, the exemplary RF system would typically include several RFreaders and multiple RF tags affixed to multiple rotor blades, with eachof the multiple RF tags functioning in the same manner in relation toeach of the several RF readers as that described for the single RF tagin relation to the single RF reader. Also, for descriptive purposes, therotor blade may be described as rotating about the central axis of theturbine engine along a “path-of-rotation”.

In accordance with exemplary embodiments, the RF reader may be suitablypositioned on a stationary surface in the turbine engine for monitoringthe RF tag. In accordance with a preferred embodiment, the RF reader isconfigured to alternate between two operating modes: a signal generatingmode (or simply, “signaling mode”); and a return signal listening mode(or simply, “listening mode”). In accordance with exemplary embodiments,the RF reader initially operates in the signaling mode. Specifically,the RF reader produces or emits an RF signal in a discrete burst orping. This RF signal or ping constitutes an RF way having a known orpredetermined frequency. Once generated, the ping travels from the RFreader toward the RF tag affixed to the rotor blade. After generatingthis ping, the RF reader switches from the signaling mode to thelistening mode.

In accordance with exemplary embodiments, the RF tag is a passive RFtag. Thus, when the RF wave of the ping reaches the RF tag, it inducesthe RF tag to emit a return RF signal. The RF tags may be configured toalter the frequency of the RF wave of the ping in the return RF signal.In accordance with exemplary embodiments, the RF tag alters thefrequency of the RF wave in a unique way so that the altered frequencyof the return RF signal identifies it as having come from the RF tag. Asstated, after generating the ping, the RF reader switched from thesignaling mode to the listening mode in order to receive the return RFsignal that is expected from the RF tag. The RF reader waits inlistening mode and receives the return RF signal from the RF tag when itarrives.

According to exemplary embodiments, a next step is to calculated a“time-of-flight” for the RF wave that traveled from the RF reader to theRF tag and back. Thus, as used herein, the time-of-flight is the timeoccurring between when the ping was sent by the RF reader and when thecorresponding return RF signal was received from the RF tag by the RFreader. To do this, the precise time at which the ping was generated bythe RF reader and the precise time at which the corresponding return RFsignal is received by the RF reader is recorded. From these two recordedevents, the time-of-flight is determined as the delay occurring betweenthem. Thus, time-of-flight represents the duration of time for the RFwave of the ping to travel from the RF reader to the RF tag plus theduration of time for the return signal to travel from the RF tag to theRF reader. Put another way, the time-of-flight is the duration of timeoccurring between generating the ping and receiving the return RFsignal. In accordance with exemplary embodiments, the time-of-flight maybe calculated by the RF reader, a computer-implemented controlleroperably connected via a communication link with the RF reader, such as,for example, the controller 200 discussed below in relation to FIG. 9,or a computer-implemented controller integrated within the RF reader,whether locally or remotely integrated, such as for example, thecontroller 200 of FIG. 9, or some combination thereof.

The method continues by repeating this “ping and listen” process inextremely short time intervals. By doing this, the time-of-flight datafor the RF tag can be collected and plotted in the time domain. As willbe appreciated, observing this time-of-flight data in the time domainwill show a decreasing time-of-flight as the RF tag on the rotor bladeapproaches the stationary RF reader, which is followed by an increasingtime-of-flight as the RF tag moves away from the stationary RF reader.In accordance with exemplary embodiments, the point at which thetime-of-flight for the RF tag reaches a minimum represents the point intime at which the RF tag has drawn closest to the RF reader as the rotorblade passes by. In accordance with exemplary embodiments, this point intime is deemed the “arrival-time” for the rotor blade or, moreparticularly, the arrival-time of the specific portion of the rotorblade to which the RF tag is affixed.

The “arrival-time” for the RF tag can be recorded by multiple RFreaders, which are configured to operate like the RF reader, as the RFtag/rotor blade revolves about the working fluid flowpath of theturbine. The “arrival-time” data gathered by the multiple RF readers canthen be input into standard blade timing algorithms to determine thevibrational response, including amplitude and frequency, of the rotorblade during operation.

For example, FIG. 6 includes a plot 195 of arrival-time data for threerotor blades having three RF tags, respectively, which are passing by astationary RF reader. The above-described “ping and listen” process maybe repeated by the RF reader and the resulting time-of-flight data forthe three rotor blades may be plotted in the time domain. As shown, inplot 195, the X-axis represents “Time” while the Y-axis represents“Time-of-Flight”. For each of the three rotor blades, the point in timeat which the RF tag comes closest to the stationary RF reader can bedetermined as the point in time that corresponds to the minimumtime-of-flight. In general, time-of-flight data plotted in the timedomain will have a general “U” or “V” shape, decreasing as the rotorblade approaches the stationary RF reader before reaching a minimumvalue, and then increasing as the rotor blade moves away. In accordancewith exemplary embodiments, the minimum time-of-flight may be determinedby mathematically estimating the minimum time-of-flight given nature ofthe time domain plot. Alternatively, the step of determining the minimumtime-of-flight may include selecting the time-of-flight having a leastvalue from among collected time-of-flight data points.

Once the minimum time-of-flight is found, the corresponding time on theX-axis can be deemed as the arrival-time for the particular rotor blade.From this, using a speed signal of the rotor or other techniques, it canthen be determined if the arrival-time of the each of the rotor bladesindicates whether it is “on-time”, “early”, or “late”, and, in regard tothe latter two, the extent to which the rotor blade is early or late. Aswill be appreciated, once such arrival-time data is known for each ofthe rotor blades, it can then be input into industry standard algorithmsfrom which is derived the vibrational response of the rotor blades,which can serve as an indicator of blade health and/or detect thepresence of defects.

In accordance with exemplary embodiments, when multiple RF tags areused, each may be configured to alter the RF signal wave to a differentfrequency in the return RF signal, which may be used to differentiatebetween multiple return signals so that a source RF tag is ascertainedfor each. The RF reader may distinguish between multiple return signalsissuing from multiple RF tags disposed on different rotor blades and/ormultiple RF tags disposed on different regions of the same rotor blade.Thus, as depicted in FIG. 6, the RF reader may receive multiple returnsignals that were sent from multiple RF tags in response to the sameping and, in each case, discern the particular RF tag to which eachcorresponds. Another advantage of the return signal frequency shift isthat if the RF reader receives an RF signal that is the same frequencyas the ping (i.e., the RF signal generated by the RF reader), it can beassumed that it is merely a reflection occurring within the turbine, andnot a return RF signal from one of the multiple tags.

Thus, for example, exemplary methods and systems for determining anarrival-time of a rotor blade may include using a “time-of-flight”criteria in conjunction with an RF reader attached to a stationarysurface and an RF tag attached to a rotor blade. During the operation ofthe turbine engine, time-of-flight data points may be collected via anRF monitoring process (also “time-of-flight RF monitoring process”) thatincludes: emitting an RF signal from the RF reader; recording a firsttime as being when the RF signal is emitted by the RF reader; receivingthe RF signal at the RF tag and emitting a return RF signal by the RFtag in response thereto; receiving the return RF signal at the RFreader; recording a second time as being when the return RF signal isreceived at the RF reader; and determining the time-of-flight data pointas being a duration occurring between the first time and the secondtime. The RF monitoring process may be repeated until multipletime-of-flight data points are collected. Then a minimum time-of-flightmay be determined from the multiple time-of-flight data points, and,from the minimum time-of-flight, the arrival-time for the rotor blade isdetermined as being a time that corresponds to the minimumtime-of-flight. In accordance with exemplary embodiments, the monitoringprocess may be repeated so that the multiple time-of-flight data pointsincludes at least: a plurality of the time-of-flight data points as therotor blade nears the RF reader; and a plurality of the time-of-flightdata points as the rotor blade moves away from the RF reader. Themultiple time-of-flight data points may include a series of thetime-of-flight data points taken sequentially during a portion of asingle revolution of the rotor blade along the path-of-rotation.Finally, the method may be repeated such that a set of arrival-timedataset is collected, wherein the dataset includes multiplearrival-times calculated for different revolutions of the rotor bladeabout the path-of-rotation, respectively. The arrival-time dataset maythen be used to calculate a vibrational response of the rotor blade.

With reference now to FIG. 7, an alternative embodiment of the presentdisclosure will now be described. As will be seen, with this embodiment,an RF system, such as the above-described RF system 180, is operated ina different manner for collecting arrival-time data for passing rotorblades. Again, for the sake of clarity, exemplary operation for thisembodiment will be described in relation to a single RF reader thatfunctions in relation to a single RF tag affixed to a single rotorblade. It should be understood, though, that several RF readers andmultiple RF tags affixed to multiple rotor blades may also be used.

In accordance with the present embodiment, the RF reader is suitablypositioned on a stationary surface in the turbine engine for monitoringthe rotor blade. In this case, however, instead of the RF reader beingconfigured to alternate between a signaling mode and a listening mode,the RF reader is configured to emit an RF signal continuously or at veryshort time intervals while, at the same time, listening continuously forthe return RF signal from the RF tag, which, as before, may be a passiveRF tag. The continuous or short interval RF signal from the RF readerinduces a similar formatted return RF signal form the RF tag, which isreceived by the RF reader, which, as stated, is listening continuously.Similar to the above-described embodiment, the RF tag may be configuredto alter the frequency of the RF wave in the return RF signal so thatthe source of the return RF signal may be determined by the RF reader.

Instead of using variations in “time-of-flight” to determinearrival-time, the present embodiment uses variations in the magnitude orsignal strength (also “strength-of-signal”) of the return RF signal. Aswill be appreciated, the signal strength of the return RF signal is afunction of several factors, including, primarily, the distance betweenthe RF tag and the RF reader. During the course of a revolution, the RFreader monitors the varying signal strength of the return RF signal andrecords the values thereof. For example, as the rotor blade moves closerto the RF reader, the signal strength of the return RF signal increasesin magnitude and, as the rotor blade moves away from the RF reader, thesignal strength decreases in magnitude. Plotting the signal strength intime domain, the shape of the curve thus resembles an upside-down “U” or“V”—the inverse of the above “time-of-flight” plot of FIG. 6.

In accordance with the present embodiment, the maximum signal strengthis used to indicate the arrival-time of the rotor blade. That is, thepoint at which the signal strength for the RF tag reaches a maximumrepresents the point in time at which the RF tag comes closest to the RFreader as the rotor blade passes by. This point in time becomes the“arrival-time” of the rotor blade or, more particularly, becomes thearrival-time of the particular region of the rotor blade to which the RFtag is affixed. As before, such “arrival-time” data can be measured andrecorded for the rotor blade by multiple RF readers positioned about theworking fluid flowpath. The “arrival-time” data collected by themultiple RF readers in this manner can then be input into standard bladetiming post-processing algorithms to determine the vibrational responseof the rotor blade.

With specific reference to FIG. 7, a plot 196 is shown of arrival-timedata for three rotor blades having three RF tags, respectively, whichare passing by a stationary RF reader. As described above, the processof continuously (or at very short intervals) emitting and listening maybe performed by the RF reader and the resulting strength-of-signal datafor the return RF signal strength of the three RF tags may be plotted inthe time domain. As indicated in the plot 195, the X-axis represents“Time” while the Y-axis represents “Return RF Signal Strength”. For eachof the three RF tags, the point in time at which each comes closest tothe stationary RF reader can be determined as the time on the X-axisthat corresponds to the maximum value of the return RF signal strength.In each case, once the maximum signal strength of the return RF signalis found, the corresponding time on the X-axis is deemed thearrival-time. From this, using a speed signal of the rotor or othertechniques, it can then be determined if the arrival-time of the rotorblade indicates whether the rotor blade is “on-time”, “early”, or“late”, and, in regard to the latter two, the extent to which the rotorblade is early or late. And, as in the above example, once sucharrival-time data is known for each of the rotor blades, it can then beinput into industry standard algorithms that derive the vibrationalresponse of each of the rotor blades, which can serve as an indicator ofblade health and/or detect the presence of defects. Finally, inaccordance with exemplary embodiments, when multiple RF tags are used,each may be configured to alter the RF signal wave to a differentfrequency, which may be used to differentiate between multiple returnsignals so that a source RF tag can be ascertained for each.

Thus, for example, exemplary methods and systems for determining anarrival-time of a rotor blade may include using a “strength-of-signal”criteria in conjunction with an RF reader attached to a stationarysurface and an RF tag attached to a rotor blade. During the operation ofthe turbine engine, strength-of-signal data points may be collected viaan RF monitoring process (also “strength-of-signal RF monitoringprocess”) that includes: emitting an RF signal from the RF reader;receiving the RF signal at the RF tag and emitting a return RF signal bythe RF tag in response thereto; receiving the return RF signal at the RFreader; measuring a signal strength of the return RF signal as receivedby the RF reader; and determining the strength-of-signal data point asbeing equal to the measured signal strength. The RF monitoring processmay be repeated until multiple strength-of-signal data points arecollected. Then a maximum strength-of-signal may be determined from themultiple strength-of-signal data points, and, from the maximumstrength-of-signal, the arrival-time for the rotor blade is determinedas being a time that corresponds to the maximum strength-of-signal. Inaccordance with exemplary embodiments, the monitoring process may berepeated so that the multiple strength-of-signal data points includes atleast: a plurality of the strength-of-signal data points as the rotorblade nears the RF reader; and a plurality of the strength-of-signaldata points as the rotor blade moves away from the RF reader. Themultiple strength-of-signal data points may include a series of thestrength-of-signal data points taken sequentially during a portion of asingle revolution of the rotor blade along the path-of-rotation.Finally, the method may be repeated such that an arrival-time dataset iscollected, wherein the arrival-time dataset includes multiplearrival-times calculated for different revolutions of the rotor bladeabout the path-of-rotation, respectively. The arrival-time dataset maythen be used to calculate a vibrational response of the rotor blade.

With reference now to FIG. 8, another embodiment of the presentdisclosure is illustrated, which will be discussed in relation to arotor blade 150 that, for example, may be a rotor blade used in theturbine section of a gas turbine or steam turbine engine. As will beseen, in this case, the RF system includes one or more reference RFtags, which are added to the system so to improve certain aspectsrelating to arrival-time data collection.

Similar to the example of above, the rotor blade 150 may have the samegeneral orienting features, which include an airfoil 152 that extendsradially between a root 155 and an outer tip 159. The airfoil 152 mayalso include a pressure side 153 and a suction side 154 extendingbetween a leading edge 156 and a trailing edge 158. As also shown inFIG. 8, the root 155 of the rotor blade 150 may connect to a rotor wheel197. Further, the root 155 includes a platform 198, which is thesubstantially flat surface from which the airfoil 152 extends. As willbe appreciated, the platforms 150 of adjacent rotor blades 150 abut todefine the inner radial boundary of the working fluid flowpath.

According to the present embodiment, one or more RF tags 160 may beaffixed to one or more locations on the rotor blade 150. In accordancewith preferred embodiments, the one or more RF tags 160 are disposed onthe airfoil 152 in regions of the airfoil 152 that are less rigid anddeflect more during operation. For example, as illustrated, an RF tag160 may be secured to: 1) the approximate mid-area of the pressure side153 of the airfoil 152 near the trailing edge 158 and 2) near the outertip 159 of the pressure side 153 of the airfoil 152 near the leadingedge 156. These locations are exemplary, as there are other locations ona rotor blade where monitoring via additional RF tags may beadvantageous.

In accordance with the present embodiment, one or more additional RFtags, which will be referred to herein as “reference RF tags 199”, areaffixed to one or more rotating components near the RF tags 160 for thepurposes of improving the performance of the blade timing systems andmethods disclosed above. According to preferred embodiments, thereference RF tags 199 may be affixed to more rigid portions of the rotorblade 150 and/or other rigid rotating structure that is near theposition of the RF tags 160. In general, as will be seen, the referenceRF tag 199 may be used to provide a baseline or reference arrival-timeagainst which the arrival-time of the other RF tags 160 may be compared.

Broadly, the reference RF tags 199 may be positioned on any rotatingstructure near one of the RF tags 160. In regard to preferred locationsfor the reference RF tag 199, as stated, these may include rigidrotating structure near the location of the RF tags 160. For example, asshown in the exemplary embodiment of FIG. 8, a first possible locationfor the reference RF tag 199 is the inner radial portion of the airfoil152. As will be appreciated, the rigidity of the airfoil 152 increasesas it nears the root 155, making this position near the root desirable.A second possible location for the reference RF tag 199 is a position onthe root 155 of the rotor blade 150. As illustrated, for example, thereference RF tag 199 may be attached to the platform 198 of the root155. Other locations on the root 155 are also possible, such as theunderside of the platform 198 or the shank portion that extends betweenthe platform 198 and a dovetail connector that is used to attach therotor blade 150 to the rotor wheel 197. A third possible location forthe reference RF tag 199 is on the rotor wheel 197. In this case, asshown, the reference RF tag 199 may be placed on the outer circumferenceof the rotor wheel 199 so that it approximately circumferentiallycoincides or aligns with the rotor blade 150 on which the RF tags arelocated. In use, the reference RF tags 199 may be utilized in the samegeneral manner described above in relation to the RF tags 160. That is,arrival-time data may be collected for the reference RF tags 199 usingeither the “time-of-flight” or “signal strength” methods.

When the arrival-time for a particular region of the rotor blade—such asthe outer tip of the airfoil—is determined (either by conventionalprobes or the RF systems described herein), there remains an additionalrequirement of knowing an actual arrival-time for the rotor blade forthe sake of comparison. In this way it can be determined if thearrival-time of the particular region is “on-time”, “early”, or “late”,and from this, the vibrational response of the rotor blade can bederived. Conventional blade timing techniques generally determine theactual arrival-time of the rotor blade by referring to a rotor speedparameter, i.e., the measured speed of the rotor wheel to which therotor blade is attached. However, there are several drawbacks to this.First, rotor speed is measured via a sensor that is part of separatecontrol system of the turbine engine and, in order to access the rotorspeed values for the purposes of blade timing requires some set-up andreconfiguration. Second, even when such communications reconfigurationis achieved, the measuring of rotor speed is a slower process thatintroduces a delay or lag to blade timing. Third, the measurement ofrotor speed is generally not as precise as desired for blade timingpurposes, which introduces level of uncertainty to the results.

With the proposed use of a reference RF tag, the need for referring torotor speed or other sensor measurements to determine the actualarrival-time of the rotor blade is removed. Specifically, the actualarrival-time of the rotor blade—against which the arrival-time of theother RF tags can be compared—is determined by the reference RF tag. Todo this, the reference RF tag is disposed on rigid rotating structurenear the other RF tags so that the reference RF tag's arrival-time canbe assumed as the real or, as used herein, “actual arrival-time” for therotor blade itself. As describe above, preferred locations for thereference RF tag include the inner radial portions of the airfoil, theplatform or root, and/or rotor wheel.

In accordance with present embodiment, RF blade timing systems of thepresent disclosure may include one or more RF readers and one or morerotor blades, which each includes one or more RF tags and one or morereference RF tags, which, for the sake of clarity, may be described withreference to a single RF reader, rotor blade, RF tag, and reference RFtag. In use, the arrival-time of the reference RF tag and the RF tag maybe calculated by the RF reader via either the time-of-flight RFmonitoring process, the strength-of-signal RF monitoring process, asdescribed above, or some other. The arrival-time calculated for thereference RF tag may be designated the actual arrival-time for the rotorblade. Then, by comparing this to the arrival-time calculated for the RFtag, it can be determined whether the RF tag arrived on-time or theextent to which it arrived early or late or, put another way, led orlagged relative to the arrival-time of the rotor blade. As will beappreciated, for example, if the RF tag is located at the outer tip, anearly or late arrival ma indicate a deflection occurring through theairfoil in response to operating vibration. Once such arrival-time datais known—i.e., the extent to which the RF tag is early, on-time, or latein relation to the reference RF tag—the data can be input into industrystandard algorithms that derive the vibrational response of the rotorblade. It should further be understood that reference RF tags may besimilarly used to compare arrival-time data between any two differentrotating components or different regions of a rotating component.

Thus, for example, exemplary methods and systems for determining anarrival-time of a rotor blade may include using a reference RF tag inconjunction with an RF reader attached to a stationary surface and an RFtag attached to a rotor blade. The RF tag may be attached to a firstregion of the rotor blade, while the reference RF tag is attached to arotating structure near the RF tag. In use—for example, in relation to afirst revolution of the rotor blade occurring during the operation ofthe turbine engine—the arrival-time for each of the RF tag and thereference RF tag may be collected with the RF reader via an RFmonitoring process, which may include the time-of-flight RF monitoringprocess or the strength-of-signal RF monitoring process. Thearrival-time of the RF tag may be compared to the arrival-time of thereference RF tag to determine an arrival-time test result for the firstregion of the rotor blade for the first revolution. In accordance withexemplary embodiments, both the RF tag and reference RF tag may bepassive. As stated above, the arrival-time of the reference RF tag maybe designated as an actual arrival-time for the rotor blade. Thearrival-time test result for the first region of the rotor blade, thus,may indicate an amount by which the arrival-time of the first region ofthe rotor blade leads or lags the designated actual arrival-time of therotor blade. The method may further include repeating the steps tocollect the arrival-time test result for the first region of the rotorblade for multiple other revolutions of the rotor blade during engineoperation. These may be compiled in a dataset of arrival-time testresults, which then may be used to calculate a vibrational response ofthe rotor blade.

As will be appreciated, the above-disclosed embodiments of the presentdisclosure may be used for blade timing studies, including upfrontvalidation testing of new rotor blade designs and in situ long-termrotor blade health monitoring. Blade timing systems and methods of thepresent disclosure can be used on both compressor rotor blades andturbine rotor blades or buckets, including turbine rotor blades in steamand combustion turbine engines, as well as any other rotatingcomponents. Unlike the hardware associated with laser probes and othersensors of conventional blade timing techniques, the RF devices requiredby the embodiments of the present disclosure are both inexpensive andapplication independent, making them reusable and further loweringimplementation costs. Additionally, the required RF devices—includingthe RF readers and RF tags—can be implemented within the harsh turbineenvironment without the need of cooling air, making regular longer termtesting feasible. Additional and related advantages include RF-basedsystems for blade timing being easier to install and implement in thefield with less initial investment. Finally, systems of the presentdisclosure can provide far more data that is richer in content and morereliable.

With reference now to FIG. 9, the RF blade timing system of the presentdisclosure may include computing and processing resources, such as acomputer-implemented control system or controller 200, which may be usedto implement certain embodiments of the present disclosure or componentsor aspects of those embodiments. For example, as indicated, thecontroller 200 may be communicatively linked to and/or integrated withthe RF readers and, thereby, receive the data collected by the RFreaders, which may include arrival-time data, time-of-flight data,and/or strength-of-signal for each of the RF tags and/or reference RFtags that are part of the RF system. The controller 200 then may processsuch data so to derive a vibrational response, performance or healthcharacteristic about the rotor blades to which the RF tags are attached.The controller 200 may be configured to automatically output the derivedrotor blade characteristic to one or more other computer systems,including at least one computer system of a predetermined user connectedwith the design and/or operation of the rotor blades, so that an actionby such user may be taken when appropriate.

As illustrated, the controller 200 may include a memory 202 that storesprogrammed logic 204 (e.g., software) and data 206. Memory 202 also mayinclude an operating system 208. A processor 210 may utilize operatingsystem 208 to execute programmed logic 204, and in doing so, may alsoutilize data 206. A control and data bus 212 may provide communicationbetween memory 202 and processor 210. Users may interface withcontroller 200 via at least one user interface device 214, such as akeyboard, mouse, touchscreen, gesture control device, wearable computer,control panel, or any other device capable of communicating data to andfrom controller 200. The controller 200 may be in communication with RFequipment and its associated devices online, including sensors or datarecorded from such sensors, while operating, as well as in communicationwith the equipment and its associated devices offline while notoperating, via an input/output (I/O) interface 216. More specifically,the controller 200 may carry out the execution of instructions for, butnot limited to, providing commands to certain devices, including RFreaders and/or its associated devices, as provided herein, and receivingdata from RF readers and/or its associated devices. The controller 200and the programmed logic 204 implemented thereby may include software,hardware, firmware, or any combination thereof.

According to example embodiments, the included figures may referencesystems, methods, processes, apparatuses, and computer program products.It should be understood that at least some of those may be implemented,at least partially, by computer program instructions, which may beloaded onto a general purpose computer, the controller 200, a specialpurpose computer, a special purpose hardware-based computer, or otherprogrammable data processing apparatus to produce a machine, such thatthe instructions, which execute on the computer or other programmabledata processing apparatus, create means for implementing thefunctionality of at least some of the methods discussed herein. Thecomputer program instructions mentioned herein may also be stored in acomputer-readable memory that can direct a computer or otherprogrammable data processing apparatus to function in a particularmanner, such that the instructions stored in the computer-readablememory produce an article of manufacture including instruction meansthat implement the function specified in the block or blocks. Thecomputer program instructions may also be loaded onto a computer orother programmable data processing apparatus to cause a series ofoperational steps to be performed on the computer or other programmableapparatus to produce a computer implemented process, such that theinstructions that execute on the computer or other programmableapparatus provide steps for implementing the functions specified in theblock or blocks. One or more components of the systems and one or moreelements of the methods described herein may be implemented through anapplication program running on an operating system of a computer. Theyalso may be practiced with other computer system configurations,including hand-held devices, multiprocessor systems, microprocessorbased or programmable consumer electronics, mini-computers, mainframecomputers, and so forth.

As one of ordinary skill in the art will appreciate, the many varyingfeatures and configurations described above in relation to the severalexemplary embodiments may be further selectively applied to form theother possible embodiments of the present disclosure. For the sake ofbrevity and taking into account the abilities of one of ordinary skillin the art, all of the possible iterations is not provided or discussedin detail, though all combinations and possible embodiments embraced bythe several claims below are intended to be part of the presentapplication. In addition, from the above description of severalexemplary embodiments, those skilled in the art likely will perceiveimprovements, changes and modifications. The appended claims areintended to cover such improvements, changes and modifications. Itshould be understood that numerous changes and modifications may be madeto the subject matter disclosed herein without departing from the spiritand scope of the invention as defined by the following claims and theequivalents thereof.

That which is claimed:
 1. A method for determining an arrival time of arotor blade in a turbine engine, the turbine engine comprising a row ofrotor blades that contains the rotor blade, wherein the rotor bladerotates about a central axis during an operation of the turbine enginealong a path of rotation, the method comprising the steps of: having aradio frequency (“RF”) reader attached to a stationary surface in theturbine engine, the stationary surface being disposed in operationalproximity to the row of rotor blades; having a radio frequencyidentification tag (“RF tag”) attached to a first region of the rotorblade; having a reference radio frequency tag (“reference RF tag”)attached to a rotating structure near the RF tag; in relation to a firstrevolution of the rotor blade occurring during the operation of theturbine engine, collecting a respective arrival time for each of the RFtag and the reference RF tag with the RF reader via an RF monitoringprocess; and comparing the arrival time of the RF tag to the arrivaltime of the reference RF tag to determine an arrival time test resultfor the first region of the rotor blade for the first revolution.
 2. Themethod of claim 1, wherein each of the RF tag and the reference RF tagcomprises a passive RF tag; and wherein the RF monitoring processcomprises one of: a time-of-flight RF monitoring process; and astrength-of-signal RF monitoring process.
 3. The method of claim 2,wherein the RF monitoring process comprises the RF reader emitting an RFsignal that induces a return RF signal in each of the RF tag andreference RF tag; wherein the RF reader emits the RF signal at a firstfrequency; and wherein: the RF tag is configured to produce the returnRF signal at a second frequency that is different from the firstfrequency; and the reference RF tag is configured to produce the returnRF signal at a third frequency that is different from the first andsecond frequencies.
 4. The method of claim 2, wherein the RF reader isattached to a stator blade in the turbine engine; and wherein therotating structure to which the reference RF tag is attached is morestructurally rigid than the first region of the rotor blade to which theRF tag is attached.
 5. The method of claim 2, wherein the rotatingstructure to which the reference RF tag is attached comprises a secondregion of the rotor blade.
 6. The method of claim 5, wherein the rotorblade comprises an airfoil that extends between a root and an outer tip,the airfoil comprising first and second areas such that the first areais closer to the outer tip than the second area; wherein: the firstregion of the rotor blade to which the RF tag is attached comprises thefirst area of the airfoil; and the second region of the rotor blade towhich the reference RF tag is attached comprises the second area of theairfoil.
 7. The method of claim 5, wherein the rotor blade comprises anairfoil and a root, wherein the airfoil extends between a base, whichforms a connection with the root, and an outer tip; wherein: the firstregion of the rotor blade to which the RF tag is attached comprises theouter tip of the airfoil; and the second region of the rotor blade towhich the reference RF tag is attached comprises the base of theairfoil.
 8. The method of claim 5, wherein the rotor blade comprises anairfoil and a root; wherein: the first region of the rotor blade towhich the RF tag is attached comprises the airfoil; and the secondregion of the rotor blade to which the reference RF tag is attachedcomprises the root.
 9. The method of 8, wherein the root of the rotorblade comprises a platform that connects to a base of the airfoil; andwherein the second region of the rotor blade to which the reference RFtag is attached comprises the platform of the root.
 10. The method of 8,wherein the root of the rotor blade comprises a shank portion thatextends between a dovetail connector and a platform, the platformconnecting the root to a base of the airfoil; wherein the second regionof the rotor blade to which the reference RF tag is secured comprisesthe shank portion of the root.
 11. The method of claim 2, wherein therotor blade comprises an airfoil and a root, wherein the airfoil extendsbetween a base, which forms a connection with the root, and an outertip, and wherein the root forms a connection with a rotor wheel; andwherein: the first region of the rotor blade to which the RF tag isattached comprises the airfoil; and the rotating structure to which thereference RF tag is attached comprises the rotor wheel.
 12. The methodof claim 2, wherein the turbine engine comprises a gas turbine engine,and the rotor blade comprises a rotor blade in a turbine section of thegas turbine engine.
 13. The method of claim 2, wherein the arrival timeof the reference RF tag is designated as an actual arrival time for therotor blade; and wherein the arrival time test result for the firstregion of the rotor blade indicates an amount by which the arrival timeof the first region of the rotor blade leads or lags the actual arrivaltime of the rotor blade.
 14. The method of claim 13, further comprisingthe steps of: repeating the steps of the method to collect the arrivaltime test result for the first region of the rotor blade for multipleother revolutions of the rotor blade occurring during the operation ofthe turbine engine; compiling a dataset that includes the arrival timetest results for the first revolution and the multiple other revolutionsof the rotor blade; and using the dataset of the arrival time testresults to calculate a vibrational response of the rotor blade duringthe operation of the turbine engine.
 15. The method of claim 13, whereinthe RF monitoring process comprises the time-of-flight RF monitoringprocess; and wherein the time-of-flight RF monitoring process includesthe steps of: emitting an RF signal from the RF reader; recording afirst time as being when the RF signal is emitted by the RF reader;receiving the RF signal at the RF tag and emitting a return RF signal bythe RF tag in response thereto; receiving the RF signal at the referenceRF tag and emitting a return RF signal by the reference RF tag inresponse thereto; receiving the return RF signal from the RF tag at theRF reader and recording a second time as being when the return RF signalfrom the RF tag is received at the RF reader; receiving the return RFsignal from the reference RF tag at the RF reader and recording a thirdtime as being when the return RF signal from the reference RF tag isreceived at the RF reader; determining a first type of time-of-flightdata point as being a duration occurring between the first time and thesecond time; determining a second type of time-of-flight data point asbeing a duration occurring between the first time and the third time;repeating the preceding steps of the time-of-flight RF monitoringprocess until multiple ones of the first type of time-of-flight datapoint and multiple ones of the second type of time-of-flight data pointare collected; determining a first minimum time-of-flight from themultiple ones of the first type of time-of-flight data point, anddetermining the arrival time for the RF tag as being a time thatcorresponds to the first minimum time-of-flight; and determining asecond minimum time-of-flight from the multiple ones of the second typeof time-of-flight data point, and determining the arrival time for thereference RF tag as being a time that corresponds to the second minimumtime-of-flight.
 16. The method of claim 13, wherein the RF monitoringprocess comprises the strength-of-signal RF monitoring process; whereinthe strength-of-signal RF monitoring process includes the steps of:emitting an RF signal from the RF reader; receiving the RF signal at theRF tag and the reference RF tag, and, in response thereto, emitting areturn RF signal by each of the RF tag and the reference RF tag;receiving the return RF signals at the RF reader from each of the RF tagand the reference RF tag; measuring a signal strength of each of thereturn RF signals as received by the RF reader; determining a first typeof strength-of-signal data point as being equal to the measured signalstrength of the return signal of the RF tag; determining a second typeof strength-of-signal data point as being equal to the measured signalstrength of the return signal of the reference RF tag; repeating thepreceding steps of the strength-of-signal RF monitoring process untilmultiple ones of the first type of strength-of-signal data point andmultiple ones of the second type of strength-of-signal data point arecollected; determining a first maximum strength-of-signal from themultiple ones of the first type of strength-of-signal data point, anddetermining the arrival time for the RF tag as being a time thatcorresponds to the first maximum strength-of-signal; and determining asecond maximum strength-of-signal from the multiple ones of the secondtype of strength-of-signal data point, and determining the arrival timeof the reference RF tag as being a time that corresponds to the secondmaximum strength-of-signal.
 17. A system for determining an arrival timeof a rotor blade in a turbine engine, the system comprising: the turbineengine having a row of rotor blades that contains the rotor blade,wherein the rotor blade rotates about a central axis during an operationof the turbine engine along a path of rotation; a radio frequency (“RF”)reader attached to a stationary surface in the turbine engine, thestationary surface being disposed in operational proximity to the row ofrotor blades; a radio frequency identification tag (“RF tag”) attachedto the rotor blade; a reference radio frequency tag (“reference RF tag”)attached to a rotating structure near the RF tag; wherein, the RFreader, RF tag, and reference RF tag are configured to: collect anarrival time for each of the RF tag and the reference RF tag with the RFreader via an RF monitoring process, each of the arrival times being inrelation to a first revolution of the rotor blade occurring during theoperation of the turbine engine; and compare the arrival time of the RFtag to the arrival time of the reference RF tag to determine an arrivaltime test result for the first region of the rotor blade for the firstrevolution.
 18. The system of claim 17, wherein the rotating structureto which the reference RF tag is attached comprises a second region ofthe rotor blade; wherein the rotor blade comprises an airfoil thatextends between a root and an outer tip, the airfoil comprising firstand second areas such that the first area is closer to the outer tipthan the second area; wherein: the first region of the rotor blade towhich the RF tag is attached comprises the first area of the airfoil;and the second region of the rotor blade to which the reference RF tagis attached comprises the second area of the airfoil.
 19. The system ofclaim 17, wherein the rotating structure to which the reference RF tagis attached comprises a second region of the rotor blade; wherein therotor blade comprises an airfoil and a root; wherein: the first regionof the rotor blade to which the RF tag is attached comprises theairfoil; and the second region of the rotor blade to which the referenceRF tag is attached comprises the root.
 20. The system of claim 17,wherein the arrival time of the reference RF tag is designated as anactual arrival time for the rotor blade; and wherein the arrival timetest result for the first region of the rotor blade indicates an amountby which the arrival time of the first region of the rotor blade leadsor lags the actual arrival time of the rotor blade; wherein, the RFreader, RF tag, and reference RF tag are further configured to: collectthe arrival time test result for the first region of the rotor blade formultiple other revolutions of the rotor blade occurring during theoperation of the turbine engine; compile a dataset that includes thearrival time test results for the first revolution and the multipleother revolutions of the rotor blade; and use the dataset of the arrivaltime test results to calculate a vibrational response of the rotor bladeduring the operation of the turbine engine.